航空学报 > 2009, Vol. 30 Issue (5): 832-836

一种新的变前掠翼无人机气动布局

刘文法,王旭,米康   

  1. 空军工程大学 工程学院
  • 收稿日期:2008-03-18 修回日期:2008-07-21 出版日期:2009-05-25 发布日期:2009-05-25
  • 通讯作者: 刘文法

A New Aerodynamic Configuration of UAV with Variable Forward-swept Wing

Liu Wenfa, Wang Xu, Mi Kang   

  1. College of Engineering, Air Force Engineering University
  • Received:2008-03-18 Revised:2008-07-21 Online:2009-05-25 Published:2009-05-25
  • Contact: Liu Wenfa

摘要: 研究了一种新的变前掠翼无人机气动布局概念,在低、亚、跨和超声速状态下可通过改变机翼的前掠角来获取最佳的气动性能。根据设计指标和翼身融合技术初步设计了其几何外形,并采用三维Navier-Stokes方程数值模拟和对比分析了5种不同任务构型的气动特性。结果表明:①在Ma=0.6巡航时,平直翼加挂副油箱构型最大升阻比为14.55,而三角翼构型仅为8.29;②在Ma=0.4机动时,45°前掠翼构型失速迎角达到38°且具有最大的升力系数2.455,较平直翼构型提高了4.9%;③在Ma=1.5高速突防时,三角翼零升阻力系数最小,比平直翼加挂副油箱构型减小了14.4%,最大升阻比提高了34.6%;④所有计算状态下俯仰力矩特性均良好。研究结果验证了变前掠翼无人机气动布局新概念的合理性和先进性,可为高性能无人机的设计提供参考。

关键词: 无人机, 变前掠翼, 气动布局, 翼身融合, 数值模拟

Abstract: A new aerodynamic configuration of unmanned aerial vehicle (UAV) with variable forward-swept wing was investigated, under which the forward-swept angle can be varied to obtain optimal aerodynamic characteristics during low, subsonic, tansonic and supersonic speeds. The basic figuration was designed according to the guidelines and blended wingbody technique, and aerodynamic characteristics of five different configurations were investigated by numerical method based on 3D Navier-Stokes equations. The results show four aspects as follows: (1) when cruising at Ma=0.6, the unswept-wing configuration with wingtip oiltank has maximal lift-drag ratio 14.55, while the delta-wing configuration is only 8.29; (2) when maneuvering at Ma=0.4, the 45° forward-swept-wing configuration has 38° stalling angle and maximal lift coefficient 2.455, which improves by 4.9% than the unswept-wing configuration; (3) when dashing at Ma=1.5, the delta-wing configuration has minimal zero-lift drag coefficient which minishes by 14.4% as compared with the unsweptwing configuration with wingtip oiltank, and the maximal lift-drag ratio improves by 34.6%; (4) the pithcing moment characteristics under all caculated states are fine. Reseach results of this article can validate that the new aerodynamic configuration is reasonable and advanced, and can also provide references for high perfomance UAV design.

Key words: unmanned aerial vehicle, variable forward-swept wing, aerodynamic configuration, blended wing-body, numerical simulation

中图分类号: